$A$ satellite is revolving in a circular orbit at a height $h$ from the Earth's surface,such that $h \ll R$,where $R$ is the radius of the Earth. Assuming that the effect of the Earth's atmosphere can be neglected,the minimum increase in the speed required so that the satellite could escape from the gravitational field of the Earth is:
- A$\sqrt{2gR}$
- B$\sqrt{gR}$
- C$\sqrt{\frac{gR}{2}}$
- D$\sqrt{gR}(\sqrt{2}-1)$
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